RU2468327C1 - Method of launching missile with laser semi-active-guidance head - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: topographical lock-on of launcher is effected with the help of satellite navigation system prior to setting the fire parameters. Fire control board with digital radio communication means is located 50-100 metres from launcher. Lock-on errors may not exceed 50 metres. Fire control parameters are transmitted in binary code to launcher ACS and, further, to missile. Launcher is turned to azimuth and elevation to launch the missile by command from control board.

EFFECT: increased range of fire, higher safety.

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Description

The invention relates to the field of armament, in particular to the control of a missile with a laser semi-active homing head, capturing the illuminated target at the end of the trajectory.

The invention is intended to control the fire of mortars and barrels of caliber type 120, 122, 152, 155 mm when firing guided ammunition, as well as guided missiles with a homing head.

A known method of firing a guided projectile with a laser semi-active homing head [Patent RU No. 2247297 of 07.24.03, - Method of firing a guided projectile with a laser semi-active homing], we have chosen for the prototype.

The scout at the control point detects and accompanies the target with a laser target designator-range finder; It transmits the coordinates of the target to the firing position, from where the firing is carried out on the tracking target with a guided projectile. After a shot, a guided projectile flies like a rocket, which captures a target illuminated by a laser beam in a finite portion of the trajectory.

The aforementioned method consists in the following: topographically sequencing the target pointer and firing position to the terrain, the target is detected by the target pointer, then the azimuth and distance from the target pointer to the target are measured and the target is topographic linked to the terrain; Calculation and implementation of firing installations by the coordinates of the target and firing position. Topographic reference of the target to the terrain and the transformation of its coordinates into a sequence of binary codes is carried out using the reconnaissance remote control, and the calculation of firing settings is carried out using the remote control firing position. At the same time, a single computer time was organized in the reconnaissance panel and in the control panel of the firing position. Next, the missile is launched and the missile is aimed at the target, which includes sequential pointing of the launcher at the target at the corners of the firing units, entering the firing settings into the missile, then launching the missile and turning the missile at the target highlighted after being shot with laser radiation from the target designator. After the rocket is launched, before the target is turned on, the firing position is transmitted from the control panel of the firing position to the reconnaissance panel via digital radio communications and the target radiation of the laser radiation is turned on, and the target illumination enable signal is automatically sent from the reconnaissance console to the target when the turn-on time is reached.

The disadvantage of this method is the limited range of firing a rocket or artillery shell (up to 20 km) and the need for combat crew launcher or guns to be close to the launcher when launching a rocket.

The objective of the invention is to increase the firing range to 50 km or more through the use of a rocket with a laser semi-active homing head, which has a marching engine, unlike an artillery shell, as well as to increase the safety of fighters for calculating the firing position by removing the firing position control panel by several tens of meters from launcher guides.

To achieve this goal in the known method of firing a guided missile with a laser semi-active homing head, which includes sequential target detection by the target, measuring the target azimuth and distance to the target, topographic binding of the target and the target to the terrain, with the topographic binding of the target carried out in the reconnaissance panel by calculation, after which, in the reconnaissance console, the coordinates of the target are converted into a sequence of binary codes and transmitted via digital radio communication to the control console the position of the firing position, the calculation of the rocket and launcher firing installations is carried out in the firing position control panel according to the coordinates of the target and the launcher, and in the reconnaissance panel and in the firing position control panel, a single computer time is set up, launch production is performed, including sequential guidance of the launcher on the target in the corners of the firing setup, entering firing installations into the missile, launching and pointing the missile at a target illuminated by laser radiation of the target designator, and the signal to turn on The electric indicator is automatically sent from the reconnaissance panel when the required turn-on time is reached, transmitted from the firing position control panel to the reconnaissance panel via digital radio communication, and the topographic location of the launcher is carried out using satellite navigation equipment of the firing position control panel; new is that, in addition, topographic reference of the launcher to the terrain using the satellite navigation equipment of the firing position control panel is performed before the firing position calculation and the firing position control panel is installed together with digital radio communications at a distance of 50-100 meters from the launcher, ensuring that the accuracy of the topographic location of the launcher, target designator and target for each measurement of the geographical coordinate system did not exceed 50 meters, calculated in the control unit the position of the firing position of the launcher and missile firing installation is transmitted in binary code to the launcher automation unit and then to the missile, the launcher is deployed at the azimuth angles and the location of the firing installations, the missile is launched according to the signal from the firing position control panel, and the launch signal missiles are transmitted to the launcher automation unit in binary code, and the delay in transmitting the signal to turn on the target indicator from the firing position control panel to the reconnaissance panel after missile launch does not exceed 3-6 ekund.

The implementation of the proposed method is illustrated in the block diagram shown in the drawing, where it is indicated: 1 - laser target designator, range finder, 2 - gyrocompass, 3 - satellite navigation equipment, 4 - reconnaissance remote control, 5 - digital radio station, 6 - firing position control panel, 7 - automation unit, 8 - rocket.

The proposed method of firing a missile with a laser semi-active homing head is implemented as follows: the firing position is located at a great distance from the line of contact with the enemy. A scout with a laser target range finder (LSC), satellite navigation equipment, a digital radio station and a reconnaissance panel is sent to the battle contact line, and the outputs of the target indicator, satellite navigation equipment and a digital radio station are connected through connectors and adapters to the processor of the reconnaissance panel.

A laser pointer with a rangefinder and a target channel serves to detect and track the target, as well as to determine the coordinates of the target, for example, the range and bearing of the target relative to the LCD.

Using satellite navigation equipment, the coordinates of the target designator in a rectangular geographic system are determined and entered into the reconnaissance console.

The scout using the LCD will measure the distance to the target and the target azimuth. The measurement results are entered into the reconnaissance panel, converted, for example, into the Earth's coordinate system of topographic location, are displayed on the reconnaissance panel screen, converted into a sequence of binary codes, for example, according to the EIA RS232C standard and transmitted to the firing position control panel via digital radio communication.

In the firing position control panel, the launcher is topographically linked to the terrain, for example, from satellite navigation equipment, coordinates for the latitude, longitude and height of the launcher are entered, data for ballistic calculations (rocket weight, charge temperature), weather data (weather bulletin or ground meteorological results).

Install the firing position control panel together with digital radio communications at a distance of 50-100 meters from the launcher. In this case, the firing position control panel is connected via cable to the launcher automation unit.

In the firing position control panel, using the radio coordinates of the target, the firing settings of the launcher and the rocket are automatically calculated. The calculation of the angles of guidance of the launcher is performed, for example, according to the dependencies given in [Patent RU No. 2111437 of 05/20/98 - The method and device for aiming guns].

Calculation of rocket firing settings may include determining the time of approach to the target and the time of switching on the homing head.

Using the gyrocompass, the launcher is aimed at the target in firing settings (in azimuth and elevation angles).

The rocket firing settings, determining the cyclogram of its flight, are transmitted in binary code to the launcher automation unit and then to the rocket's storage device.

Fighters calculating the firing position deploy the launcher, introduce firing installations into the rocket, and then take cover in a trench (dugout) 50-100 meters from the launcher; from there a rocket launch is conducted.

After that, through a voice communication channel, a report on the readiness of the launcher for launch is transmitted to the control and observation post where the deputy commander is located. From the control point on the voice communication channel the command "Start" is given. According to this command, a rocket is launched at a firing position.

Before launch, the launcher automation unit generates the voltages necessary to implement the rocket launch sequence diagram.

At the time of launch, the commander switches on the Start button on the firing position control panel and a message is automatically generated about the launch to the reconnaissance panel. At the same time, the shot time is read from the clock of the single time system from the firing position control panel and the delay time of the LCD on the target illumination mode is assigned, taking into account the total flight time of the rocket. The value of the turn-on time of the target illumination is transmitted to the reconnaissance console in the form of a sequence of binary codes.

The scout through the LCD continues to accompany the target, keep it at the crosshairs of the sighting channel.

The time of turning on the laser illuminator is automatically set in the reconnaissance console, based on the indications of the unified time of the firing position control panel and the reconnaissance panel. At the corresponding moment in time, the signal from the reconnaissance panel is issued via a digital interface, for example RS232, in the LCD and the laser beam illuminates the target.

After the launch of the rocket launcher can be moved to the stowed position and transported to a new position.

As the rocket approaches the target, the homing head on the rocket scans the earth's surface in search of a trace of the laser beam. When a laser spot is detected in a guided missile, rudder commands are generated that ensure that the rocket turns into the center of the laser spot.

The turn-on time of the laser designator can be selected constant and equal to, for example, 12 seconds before the rocket approaches the target. With this inclusion of illumination of the target for a fixed period of time before meeting the target, the operation of the missile control system is easier organized. To turn on the LCD on the backlight before the rocket reaches the target, it was established that the delay in transmitting the signal to turn on the LCD should not exceed 3-6 seconds.

Coordinate transformations in this method can be performed using the following coordinate systems.

Snapping to the LCD area and the firing position is desirable to make in the geographical coordinate system (SC) with the fixation of latitude, longitude and altitude.

LCD detects the target in the polar SC with measuring the range and angle of guidance of the LCD. In the reconnaissance console, the coordinates of the target entered from the LCD are converted to a geographical SK. Through radio communication, the coordinates of the topographic location of the target in the geographical SK are transmitted to the firing position control panel.

In the control panel firing position on the coordinates of the target and firing position determine the distance to the target, elevation, and also calculate the settings of firing in the polar SK associated with the launcher; moreover, the X axis of the coordinate system is oriented to the north. On these coordinates induce a launcher.

A missile in the first phase during a flight with a marching engine moves along a trajectory determined by the guidance of the launcher. In the second section, after turning on the homing head, the missile is controlled in the polar SK connected with the longitudinal axis of the missile.

To implement the method, the following devices can be used.

As a laser target designator, rangefinder, gyrocompass, satellite navigation equipment, reconnaissance panel, digital radio station and firing position control panel, the devices described in the prototype can be used [Patent RU No. 2247297 of 07.24.03. - A method of firing a guided projectile with a laser semi-active homing head].

The automation unit of the Hermes-A complex described in [Helicopter-based WTO Multipurpose Missile System, KBP Horizons, No. 3, 2007, pp. 36-38] can be used as an automation unit.

As a launcher, the launcher described on page 365 in the book [High-precision weapons of foreign countries. Volume 1. Anti-tank missile systems: a review and analytical guide. / Instrument Design Bureau - Tula: Bedretdinov & Co. Publishing House, 2008].

The missile is described on page 38 of the publication [Helicopter-based WTO multi-purpose missile system, KBP Horizons, No. 3, 2007, pp. 36-38].

The proposed method of firing a rocket with a laser semi-active homing head in comparison with the prototype allows to increase the firing range of the rocket and increase the safety of the launcher at the firing position. The effectiveness of the proposed method of firing is confirmed on the integrated modeling stand of the enterprise.

Claims (1)

A method of firing a guided missile with a semi-active laser homing head, which includes sequential target detection by a target, measuring the target azimuth and distance to the target, topographic binding of the target and the target to the terrain, and topographic target binding is carried out in the reconnaissance console by calculation, and then in the reconnaissance console the target coordinates convert into a sequence of binary codes and transmit them via digital radio communication to the firing position control panel, calculation of the settings The missiles and the launcher are executed in the control panel of the firing position according to the coordinates of the target and the launcher, and in the reconnaissance panel and in the control panel of the firing position they establish a unified computer time, launch production is carried out, including sequential guidance of the launcher at the target at the firing angles, input installations firing a rocket, launching and pointing the missile at a target illuminated by laser radiation of the target, and the signal to turn on the target is automatically sent from the remote and the scout when reaching the required turn-on time, transmitted from the firing position control panel to the scout’s panel via digital radio communications, and the topographic reference of the launcher is performed using satellite navigation equipment of the firing position control panel, characterized in that the topographic reference of the launcher to the terrain using the equipment the satellite navigation of the firing position control panel is performed before calculating the firing settings and the firing position control panel is installed together those with digital radio communications at a distance of 50-100 m from the launcher, ensure that the accuracy of the topographic location of the launcher, target designator and target for each measurement of the geographic coordinate system does not exceed 50 m, calculated in the firing position control panel of the firing position of the launcher and missile transmit in binary code to the automation unit of the launcher and then to the rocket, deploy the launcher at the angles of azimuth and the location of the firing installations, launch the rocket by a signal from the remote control systematic way firing position, the signal on the missile launch is transmitted to the starting automation unit installed in binary code, and transmitting the signal to switch to the firing position designator control unit delay in remote reconnaissance missiles after the launch does not exceed 3-6 seconds.